Accession Number:
AD0374199
Title:
DUAL-CHAMBER CONTROLLABLE SOLID PROPELLANT ROCKET MOTOR. VOLUME I - RESEARCH AND DEVELOPMENT EFFORTS
Descriptive Note:
Annual rept. no. 3 for fiscal year 1964
Corporate Author:
NORTHROP CAROLINA INC ASHEVILLE NC
Personal Author(s):
Report Date:
1965-11-01
Pagination or Media Count:
485.0
Abstract:
The development of propellants for the forward and aft grains was completed by means of laboratory evaluations and subscale motor tests. Present technology was demonstrated by testing full-scale motors containing 300 lb of propellant both at sea-level and altitude. Excellent results were achieved in these tests in which the motors were programmed for both pulse and throttling operation. Thrust ratios as high as 9 to 1 were achieved. Another full-scale test series was conducted to demonstrate the technology advancements made throughout the entire three-year effort. These motors contained the advanced propellants developed during the program, an improved control valve and control system, and nozzles specifically designed for on-off motor operations. Tests of these 300-lb motors were conducted both at sea level and altitude. One of these motors demonstrated nine stop-restart cycles at altitude conditions. A full- scale test that fully demonstrated the feasibility of adapting the DCCSR concept to a post-boost propulsion system was also conducted.
Descriptors:
- *SOLID PROPELLANT ROCKET ENGINES
- THROTTLING
- VOLUME
- CONTROL SYSTEMS
- FEASIBILITY STUDIES
- PULSES
- MODEL TESTS
- PRESSURE
- HIGH ALTITUDE
- COMBUSTION CHAMBERS
- IGNITION
- VALVES
- BURNING RATE
- STARTING
- THRUST
- ROCKET PROPELLANT GRAINS
- SPECIFIC IMPULSE
- CAPTIVE TESTS
- LOW ALTITUDE
- ROCKET NOZZLES
- ALUMINIZED EXPLOSIVES
- PURGING
- THRUST TERMINATION SYSTEMS
Subject Categories:
- Solid Propellant Rocket Engines
- Solid Rocket Propellants